双发进气道抽吸试验系统及流量高精度测量技术
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摘要
针对常规进气道试验方法存在流量测量精度低、综合试验能力差等诸多问题,及无法满足不同类型进气道在不同工况下开展性能试验的需要的状况,建立了一套应用于TBCC等双发发动机进气道风洞试验的抽吸试验系统及流量高精度测量技术。系统采用文氏流量计测量方法,以提高进气道流量测量的精度;采用在流量计末端直接加装中压环形引射器抽吸进气道主气流的方法,以满足不同类型进气道在不同工况下对吸入流量的需求;通过设计两套独立的管道系统并分别进行流量的测量与控制,以满足双发进气道不同工况性能匹配和耦合试验的需求。通过风洞验证试验验证了流量计的测量效果和引射器的引射能力,通过风洞应用试验验证了试验系统对不同形式进气道的综合试验能力。试验结果表明,试验系统测量精度高,引射抽吸能力和综合试验能力强,能全面满足各类进气道风洞试验的需求。
Inlet test in wind tunnel is a primary approach to evaluate the performance and obtain the characteristic parameters of the inlet.Traditional inlet test technique has some obvious problems,such as low mass flow measurement precision,and inferior test capability,cannot satisfy the inlet tests of different kinds or at different states.The pumping system and mass flow measuring technique of high precision for double-inlet wind tunnel test is established in the FD-12 wind tunnel.The mass flow measuring device using venturi measuring method is introduced to advance the mass flow measurement precision.The mass flow inbreathed by the inlet is increased by means of middle-pressure annular pumping device set at the exit of the mass flow measuring device to satisfy the inlet tests of different kinds or at different states.Two flowpaths were designed to measure and control the mass flow separately,so that the system can satisfy the performance matching and coupling test of double inlets at different states.Wind tunnel tests show that the effectiveness of the measuring device and pumping capability of the pumping device are testified,and the general test capability for inlets of different kinds is also validated.The test results show that the test system is of high measuring precision,strong pumping and wide test capability,and the corresponding technique may satisfy almost all kinds of inlet tests in wind tunnel.
Inlet test in wind tunnel is a primary approach to evaluate the performance and obtain the characteristic parameters of the inlet.Traditional inlet test technique has some obvious problems,such as low mass flow measurement precision,and inferior test capability,cannot satisfy the inlet tests of different kinds or at different states.The pumping system and mass flow measuring technique of high precision for double-inlet wind tunnel test is established in the FD-12 wind tunnel.The mass flow measuring device using venturi measuring method is introduced to advance the mass flow measurement precision.The mass flow inbreathed by the inlet is increased by means of middle-pressure annular pumping device set at the exit of the mass flow measuring device to satisfy the inlet tests of different kinds or at different states.Two flowpaths were designed to measure and control the mass flow separately,so that the system can satisfy the performance matching and coupling test of double inlets at different states.Wind tunnel tests show that the effectiveness of the measuring device and pumping capability of the pumping device are testified,and the general test capability for inlets of different kinds is also validated.The test results show that the test system is of high measuring precision,strong pumping and wide test capability,and the corresponding technique may satisfy almost all kinds of inlet tests in wind tunnel.
引文
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[17]Liao D X,Ren Z B,Yu Y S,et al.Design and experiment of constant-pressure mixing ejector[J].High Power Laser and Particle Beams,2006,18(5):728-732.(in Chinese)廖达雄,任泽斌,余永生,等.等压混合引射器设计与实验研究[J].强激光与粒子束,2006,18(5):728-732.
[18]Emanuel G.Optimum performance for a single-stage gaseous ejector[J].AIAA Journal,1974,14(9):1292-1296.
[19]Keenan J H,Neumann E P,Lustwerk F.An investigation of ejector design by analysis and experiment[J].Journal of Applied Mechanics,1950,17:299-809.
[20]Hickmank E,Hill P G,Gilbert G B.Analysis and testing of compressible flow ejectors with variable area tubes[J].ASME Journal of Basic Engineering,1972,94:407-416.
[21]Liu Z C.Aerodynamic and structural design of high and low speed wind tunnel[M].Beijing:National Defense Industry Press,2003:261-278.(in Chinese)刘政崇.高低速风洞气动与结构设计[M].北京:国防工业出版社,2003:261-278.
[2]Yang A L,Xia Y,Guo R W,et al.An investigation on design and performance for a submerged air intake[J].Acta Aerodynamica Sinica,1998,16(2):154-161.(in Chinese)杨爱玲,夏阳,郭荣伟,等.埋入式进气道的设计及其气动性能研究[J].空气动力学学报,1998,16(2):154-161.
[3]Yu A Y,Guo R W,Sun S,et al.Air-admission mechanism and low speed tunnel test of a submerged inlet with low RCS missile body[J].Acta Aerodynamica Sinica,2003,21(2):182-188.(in Chinese)余安远,郭荣伟,孙姝,等.一种隐身外形弹体下埋入式进气道的进气机理与低速实验研究[J].空气动力学学报,2003,21(2):182-188.
[4]Zhang H J,Guo R W,Li B,et al.Research status of TBCC inlet and its key technologies[J].Acta Aerodynamica Sinica,2010,28(5):613-619.(in Chinese)张华军,郭荣伟,李博.TBCC进气道研究现状及其关键技术[J].空气动力学学报,2010,28(5):613-619.
[5]Cockrell C E,Auslender A H,Guy R W,et al.Technology road map for dual-mode scramjet propulsion to support spaceaccess vision vehicle development[R].AIAA 2002-5188.
[6]Utaka Y,Taneda H,Murakami A,et al.The aerodynamic design and wind tunnel tests of a combined intake for a supersonic transport[R].ISABE-1997-7139.
[7]Albertson C W,Saied E,Trexler C A.Mach 4test results of a dual-flowpath,turbine based combined cycle inlet[R].AIAA2006-8138.
[8]Snyder L E,Escher D W,Gutierrez J L.Turbine based combination cycle(TBCC)propulsion subsystem integration[R].AIAA 2004-3649.
[9]Takayuki K,Nobuhiro T,Tetsuya S,et al.Development study on axisymmetric air inlet for ATREX engine[R].AIAA 2001-1895.
[10]Yun Q L.Testing aerodynamics[M].Beijing:National Defense Industry Press,1991:252-257.(in Chinese)恽起麟.实验空气动力学[M].北京:国防工业出版社,1991:252-257.
[11]Yun Q L.Wind tunnel testing[M].Beijing:National Defense Industry Press,2000:152-169.(in Chinese)恽起麟.风洞实验[M].北京:国防工业出版社,2000:152-169.
[12]Li Z F.Special test technology for wind tunnel[M].Beijing:Aviation Industry Press,2010:23-37.(in Chinese)李周复.风洞特种试验技术[M].北京:航空工业出版社,2010:23-37.
[13]Fan J C,Hua J,Yu K L,et al.A test technique for submerged inlet model in FL-24wind tunnel[J].Journal of Experiments in Fluid Mechanics,2008,22(1):92-94.(in Chinese)樊建超,华杰,于昆龙,等.FL-24风洞埋入式进气道试验技术[J].实验流体力学,2008,22(1):92-94.
[14]Zhang S W,Guan X D,Zhu T,et al.Measurement and calibration technique development of flow coefficient of inlet model[C]//Proceedings of the Ninth National Conference on Experimental Fluid Mechanics.Hangzhou:Chinese Society of Theoretical and Applied Mechanics,2013:509-515.(in Chinese)张绍武,关祥东,朱涛,等.进气道流量系数测量及校准技术研究[C]//第九届全国实验流体力学学术会议论文集.杭州:中国力学学会,2013:509-515.
[15]Hu P J.The pressure-drop coefficient of damping screens and its influence on the turbulence intensity of the airstream[J].Journal of Anhui Institute of Mechanical&Electrical Engineering,1999,14(1):31-34.(in Chinese)胡培杰.阻尼网的压降系数及对管道气流的影响[J].安徽机电学院学报,1999,14(1):31-34.
[16]Zou J J,Zhou J,Xu W W,et al.Experiment investigation on the start performance of the supersonic annular air ejector[J].Journal of National University of Defense Technology,2008,30(1):1-4.(in Chinese)邹建军,周进,徐万武,等.超声速环形引射器空气引射启动特性试验[J].国防科技大学学报,2008,30(1):1-4.
[17]Liao D X,Ren Z B,Yu Y S,et al.Design and experiment of constant-pressure mixing ejector[J].High Power Laser and Particle Beams,2006,18(5):728-732.(in Chinese)廖达雄,任泽斌,余永生,等.等压混合引射器设计与实验研究[J].强激光与粒子束,2006,18(5):728-732.
[18]Emanuel G.Optimum performance for a single-stage gaseous ejector[J].AIAA Journal,1974,14(9):1292-1296.
[19]Keenan J H,Neumann E P,Lustwerk F.An investigation of ejector design by analysis and experiment[J].Journal of Applied Mechanics,1950,17:299-809.
[20]Hickmank E,Hill P G,Gilbert G B.Analysis and testing of compressible flow ejectors with variable area tubes[J].ASME Journal of Basic Engineering,1972,94:407-416.
[21]Liu Z C.Aerodynamic and structural design of high and low speed wind tunnel[M].Beijing:National Defense Industry Press,2003:261-278.(in Chinese)刘政崇.高低速风洞气动与结构设计[M].北京:国防工业出版社,2003:261-278.